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EP2410131B1 - Rotor d'une turbomachine - Google Patents

Rotor d'une turbomachine Download PDF

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Publication number
EP2410131B1
EP2410131B1 EP11161987.0A EP11161987A EP2410131B1 EP 2410131 B1 EP2410131 B1 EP 2410131B1 EP 11161987 A EP11161987 A EP 11161987A EP 2410131 B1 EP2410131 B1 EP 2410131B1
Authority
EP
European Patent Office
Prior art keywords
rotor
coupling element
blade
axial direction
radially
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Not-in-force
Application number
EP11161987.0A
Other languages
German (de)
English (en)
Other versions
EP2410131A2 (fr
EP2410131A3 (fr
Inventor
Tilmann Dr. Raible
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Everllence SE
Original Assignee
MAN Diesel and Turbo SE
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by MAN Diesel and Turbo SE filed Critical MAN Diesel and Turbo SE
Publication of EP2410131A2 publication Critical patent/EP2410131A2/fr
Publication of EP2410131A3 publication Critical patent/EP2410131A3/fr
Application granted granted Critical
Publication of EP2410131B1 publication Critical patent/EP2410131B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F05D2250/73—Shape asymmetric

Definitions

  • the invention relates to a rotor of a turbomachine according to the preamble of claim 1.
  • a rotor of a turbomachine in particular a gas turbine or steam turbine, has a rotor base body and a plurality of rotor blades which are fastened to the rotor base body.
  • the blades of such a turbomachinery rotor have a blade root and an airfoil, each blade being secured via its blade root to the rotor body in a groove of the rotor body in a mounting direction defined by the blade roots, and each blade having at least one coupler segment in the region of its airfoil when it is positioned radially outward on the airfoil, is formed as an outer shroud segment.
  • the coupling element segments, in particular outer shroud segments, of all the moving blades of such a turbomachine rotor together form at least one coupling element closed in the circumferential direction, in particular an outer shroud, of the rotor.
  • a width of a coupling element segment, in particular an outer shroud segment, of each blade is defined by edges extending substantially in the axial direction.
  • a depth in the axial direction of the coupling element segment, in particular the outer shroud segment, of each blade is defined by substantially circumferentially extending edges.
  • a coupling element segment, in particular an outer shroud segment, each blade is also characterized by a thickness in the radial direction.
  • Turbomachine rotors whose rotor blades have such coupling element segments for forming at least one coupling element can be installed both in the region of a compressor and in the region of a turbine of the turbomachine.
  • Turbomachinery rotors on the rotor base body of which rotor blades are fastened, which have a coupling element segment formed radially on the outside of the airfoil as an outer cover band segment, are for example made DE 1 159 965 C , out DE 40 15 206 C1 as well as out US 4,400,915 A and from GB 2 072 760 A known. From the EP 1 134 359 A1 and the DE 1 122 551 C the attachment of the blades on the blade roots on the rotor base body in a groove of the rotor base body in a mounting direction defined by the blade feet is known. The blade feet may be fir-tree-like, hammerhead-like or otherwise contoured. For each blade root, a separate groove may be present on the rotor body. Furthermore, it is possible that all blade roots are mounted in a common groove and threaded into this common groove via a threading and thus mounted on the rotor body.
  • the coupling elements of such turbomachinery rotors designed as outer shrouds are exposed to high loads during operation, since they rotate with respect to a rotational axis of the turbomachine rotor to a maximum radius and are therefore exposed to high centrifugal forces.
  • corners or edges of the coupling element segments of the blades can bend outwards, which on the one hand in the coupling element voltage spikes are caused and on the other hand, a desired contact between adjacent coupling element segments adjacent blades is reduced to a punctiform contact or disappears completely.
  • a desired coupling between adjacent coupling element segments is reduced or eliminated, which ultimately worsens the vibration behavior of the turbomachine rotor.
  • the present invention is based on the problem to provide a rotor of a turbomachine, in which a good coupling of the coupling element segments of the blades is ensured with good mountability of the rotor during operation.
  • a rotor according to claim 1.
  • the or each coupling element segment of each blade on a first side, in the circumferential direction, a coupling element segment of a first immediately adjacent blade connects, and at one on one of the first side opposite the second side, seen in the circumferential direction, a coupling element segment a second immediately adjacent blade adjoins, contoured such that on the first side and on the second side of a substantially axially extending radially outer edge and a substantially axially extending radially inner edge of the respective coupling element segment each two separated by a dividing line Limiting surfaces, wherein at at least one circumferential position of the rotor between two directly adjacent blades formed on immediately adjacent sides of the coupling element segments dividing lines of these immediately adjacent In some other circumferential position between two directly adjacent blades formed on immediately adjacent sides of the coupling element segments dividing lines of these immediately adjacent blades to the mounting direction of the blades on the rotor blades at approximately approximately parallel or rectified to the plane defined
  • the contouring of the coupling element segments of the rotor blades ensures optimum support and thus coupling of the coupling element segments forming the or each coupling element with good mountability of the rotor.
  • the present invention relates to a rotor of a turbomachine, in particular a rotor of a compressor or a turbine of a turbomachine designed as a gas turbine or steam turbine.
  • a rotor of a turbomachine in particular a rotor of a compressor or a turbine of a turbomachine designed as a gas turbine or steam turbine.
  • the invention is not limited to these applications, but the invention can be used in all turbomachinery rotors.
  • a rotor of a turbomachine basically has a rotor main body and a plurality of rotor blades, which are fastened to the rotor base body via blade feet.
  • the rotor body and the blade roots of blades are not shown in detail since these details are familiar to those skilled in the art.
  • each blade is fastened via its blade root on the rotor base body in a groove of the rotor base body in a mounting direction defined by the blade feet.
  • a separate groove on the rotor base body may be present for each blade or the blade root of each blade.
  • it is possible that all blades are fastened via their blade roots in a common groove and are threaded into this common groove via a threading opening and thus mounted on the rotor base body.
  • the mounting direction M of the blades on the rotor base body defined by the blade feet is shown schematically in dashed lines.
  • the mounting direction M rectilinear
  • the mounting direction M is curved.
  • the mounting direction M of the blades is inclined with respect to the axial direction A in a first orientation in the circumferential direction U, wherein the mounting direction M and the axial direction A include a so-called rhomboid angle, which in a curved mounting direction M in the axial direction A changed.
  • a radial direction R of the same is furthermore shown.
  • FIG. 1 to 4 show different detail views of a rotor according to the invention of a turbomachine according to a first embodiment of the invention, wherein in Fig. 1 3 shows a section of a coupling element designed as an outer cover strip, which is composed of coupling element segments 10, 10 ', 10 "of a plurality of moving blades formed as outer cover tape segments
  • the outer cover tape segments 10, 10', 10" are, as best 3 and 4 can be removed, is associated with a radially outer end of a blade 11 of the respective blade.
  • the airfoil 11 has a flow inlet edge 12, a flow outlet edge 13 and a suction side 14 and pressure side 15 extending between the flow inlet edge 12 and the flow outlet edge 13.
  • the outer shroud segment 10, 10 ', 10 "radially outwardly assigned to the blade 11 of each blade has a width in the circumferential direction U, which is defined by edges extending substantially in the axial direction A.
  • radially outer edge 18 and 19 on two opposite sides 16 and 17 of FIG Outer shroud segment 10, 10 ', 10 "in each case one extending substantially in the axial direction A, radially outer edge 18 and 19 and in each case also extending substantially in the axial direction A, radially inner edge 20 and 21.
  • the distance between this radially outer edge 18 and 19 and this radially inner edge 20 and 21 determined on the sides 16 and 17 in the radial direction R, the thickness of the outer shroud segment 10, 10 ', 10 ".
  • a depth in the axial direction A of the outer shroud segment 10, 10 ', 10 "of each blade is defined by edges extending substantially in the circumferential direction U, again by radially outer edges 22 and 23 and radially inner edges 24 and 25, respectively the edges at the edges 22 and 24 are flow-entry-side edges and edges at the edges 23 and 25.
  • the distance between these edges also determines the thickness of the outer shroud segment 10, 10 ', 10 "in the radial direction R, namely the flow inlet side and the flow outlet side.
  • the radially inner edge 20 of the outer shroud segment 10, 10 ', 10 "extending substantially in the axial direction A is opposite the radially outer edge 18, which also extends substantially in the axial direction A. Circumferential direction U before.
  • second side 17 of the outer shroud segment 10, 10 ', 10 " at which an immediately adjacent, second blade with its outer shroud segment, namely with a first side thereof, followed, the same is contoured such that the flow outlet side adjacent to the flow outlet edge 13 of the airfoil 11 which extends substantially in the axial direction A extending, radially outer edge 19 of the outer shroud segment 10, 10 ', 10 "relative to the also extending substantially in the axial direction A, radially inner edge 21 in the circumferential direction U protrudes.
  • the surface 28, which is concealed from the outside is positioned on the flow inlet side and the surface 30, which is visible from the radial outside, is positioned on the outlet side in the region of the opposite, second side 17 of the outer shroud segment 10, 10', 10 on the other hand, the surface 29, which is concealed radially from the outside, is positioned on the flow exit side and the surface 31, which is visible from the radial outside, is positioned on the flow inlet side.
  • the parting lines 26, 27 of these immediately adjacent moving blades are approximately parallel or rectified to the mounting direction M defined over the blade roots on immediately adjacent sides of the respective coupling element segments 10 'and 10 " of the rotor blades at the rotor base body, whereas at each other circumferential position between two directly adjacent rotor blades the separating lines 26, 27 of these immediately adjacent blades are inclined to the mounting direction M on immediately adjacent sides of the respective coupling element segments 10, 10 'and 10 ".
  • the mounting direction M of the rotor blades is inclined relative to the axial direction A in a first orientation in the circumferential direction U about the so-called rhomboid angle.
  • the parting lines 26, 27 are inclined in a direction opposite to the first orientation second orientation as the mounting direction M relative to the axial direction in the circumferential direction.
  • the above contouring of the coupling element segments 10, 10 'and 10 "of the rotor blades ensures optimal support and thus coupling of the coupling element segments forming the or each coupling element with good mountability of the rotor Coupling element segments 10, 10 'and 10 "are inclined to the mounting direction M, an optimal support and thus coupling of the coupling element segments.
  • the radially outer edges 18, 19, which extend essentially in the axial direction A, and the radially inner edges 20, 21, which also extend essentially in the axial direction A, preferably run together with the dividing lines 26, 27, the surfaces 28, 29, 30 and 31 limit.
  • the dividing lines 26 and 27 which separate the surfaces 28 and 30 and the surfaces 29 and 31 from each other on the first side 16 and on the second side 17 are executed according to a preferred embodiment of the invention without turning points, wherein the same in the embodiment of Fig. 1 to 4 straight and in Fig. 5 curved. This allows a particularly simple production. Likewise, the substantially extending in the axial direction A edges 18, 19, 20 and 21 are executed without turning points.
  • dividing line 26 of the first side 16 is visible from radially outside, whereas the dividing line 27 of the second side 17 is hidden from the outside when viewed radially.
  • the dividing lines 26 and 27 of the two sides 16, 17, starting from the flow inlet-side edges to flow-outlet-side edges, run in each case from radially outside to radially inside.
  • first side 16 of the outer shroud segment 10 and the opposite, second side 17 of the outer shroud segment 10 are seen in the direction along the respective parting line 26 and 27 viewed from radially outside surfaces 28 and 29 and the visible from radially outside surfaces 30th or 31 each with respect to the radial direction R inclined at an angle.
  • the surfaces 28 and 29, which are concealed radially from the outside are inclined by a first angle relative to the radial direction R and the surfaces 30 and 31, which are visible from the radially outside, are inclined by a second angle relative to the radial direction R.
  • the first angle and the second angle are equal in magnitude, but have different signs. This is particularly advantageous in terms of manufacturing technology. In contrast to this, however, it is also possible for the first angle and the second angle to be different in magnitude on the first side 16 and on the second side 17, but in turn have different signs.
  • FIG. 1 How best Fig. 1 can be removed, as viewed from radially outside both on the first side 16 and on the second side 17 of the outer shroud segment 10 extending substantially in the axial direction A, radially outer edge 18 and 19 and which are substantially in the axial direction A extending, radially inner edge 20 and 21 congruent only at an axial position.
  • Fig. 1 to 4 are formed on the sides 16 and 17 of the outer shroud segment 10 surfaces 28 and 29 and the surfaces 30 and 31 respectively formed as a three-dimensional contoured, spatially radially curved. Essentially radially extending edges 32 bounding the outer shroud segment 10 together with the edges 18, 19, 20, 21, 22, 23, 24, and 25 are then curved.
  • these surfaces 28, 29, 30 and 31 are designed as two-dimensionally contoured, flat surfaces. Essentially radially extending edges 32 bounding the outer shroud segment 10 together with the edges 18, 19, 20, 21, 22, 23, 24 and 25 are then straight.
  • the embodiment differs from the Fig. 5 from the embodiment of Fig. 1 to 4 only in that the mounting direction M of the blades is not rectilinear but curved.
  • the embodiment of the Fig. 5 with the embodiment of Fig. 1 to 4 match, so that reference is made to the above statements.
  • a rotor according to the invention has no outer shroud segment but exclusively at least one coupling element segment embodied as an inner coupling element segment. Furthermore, it is possible for the parting line 26 of the first side 16 to be concealed from radially outside, whereas the parting line 27 of the second side 17 is visible from radially outside.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (15)

  1. Rotor d'une turbomachine, comportant un corps de base de rotor et plusieurs pales de rotor, dans lequel chaque pale de rotor présente un pied de pale et une pale, dans lequel chaque pale de rotor est fixée par l'intermédiaire de son pied de pale sur le corps de base de rotor dans une rainure du corps de base de rotor dans une position de montage définie au-dessus des pieds de pale, dans lequel chaque pale de rotor présente au niveau de sa pale au moins un segment d'élément de couplage (10, 10', 10"), et dans lequel dans la direction circonférentielle une largeur du ou de chaque segment d'élément de couplage (10, 10', 10") d'une arête s'étendant essentiellement dans la direction axiale de chaque pale de rotor est définie, caractérisé en ce que le ou chaque segment d'élément de couplage (10, 10', 10") de chaque pale de rotor sur un premier côté (16), auquel vu dans la direction circonférentielle un segment d'élément de couplage d'une première pale de rotor directement voisine se rattache, et sur un deuxième côté (17) opposé à un des premiers côtés (16), auquel vu dans la direction circonférentielle un segment d'élément de couplage d'une deuxième pale de rotor directement voisine se rattache, présente un contour tel que sur le premier côté (16) et sur le deuxième côté (17), l'arête extérieure radiale (18,19) s'étendant essentiellement dans la direction axiale et l'arête intérieure radiale (20, 21) s'étendant essentiellement dans la direction axiale du segment d'élément de couplage définissent respectivement deux surfaces séparées l'une de l'autre par une ligne de séparation (26,27), dans lequel sur au moins une position circonférentielle du rotor entre deux pales de rotor directement voisines, les lignes de séparation (26,27) réalisées sur les côtés directement voisins (16,17) des segments d'élément de couplage (10', 10") de ces pales de rotor directement voisines s'étendent approximativement parallèlement, resp. en alignement dans la même direction par rapport à la direction de montage définie au-dessus des pieds de pale des pales de rotor sur le corps de base de rotor, tandis que à chaque autre position circonférentielle entre deux pales de rotor directement voisines les lignes de séparation (26,27) réalisées sur les côtés directement voisins des segments d'élément de couplage (10, 10', 10") de ces pales de rotor directement voisines sont inclinées par rapport à la direction de montage.
  2. Rotor selon la revendication 1, caractérisé en ce que sur la ou chaque position circonférentielle du rotor, à laquelle les lignes de séparation (26,27) réalisées sur les pales de rotor directement voisines s'étendent approximativement parallèlement, resp. en alignement dans la même direction par rapport à la direction de montage définie au-dessus des pieds de pale des pales de rotor sur le corps de base de rotor, les lignes de séparation (26,27) définissent avec la direction de montage un angle maximal de 10°.
  3. Rotor selon la revendication 2, caractérisé en ce que sur la ou chaque position circonférentielle du rotor, à laquelle les lignes de séparation (26,27) réalisées sur les pales de rotor directement voisines s'étendent approximativement parallèlement, resp. en alignement dans la même direction par rapport à la direction de montage définie au-dessus des pieds de pale des pales de rotor sur le corps de base de rotor, les lignes de séparation (26,27) définissent avec la direction de montage un angle maximal de 5°.
  4. Rotor selon une des revendications 1 à 3, caractérisé en ce que la direction de montage des pales de rotor sur le corps de base de rotor vu dans la direction axiale par rapport à la direction axiale dans une première orientation est incliné dans la direction circonférentielle, dans lequel sur la ou chaque position circonférentielle du rotor, à laquelle les lignes de séparation (26,27) réalisées sur les pales de rotor directement voisines s'étendent approximativement parallèlement, resp. en alignement dans la même direction par rapport à la direction de montage définie au-dessus des pieds de pale des pales de rotor sur le corps de base de rotor, les lignes de séparation (26,27) sont inclinées dans la même orientation que la direction de montage par rapport à la direction axiale dans la direction circonférentielle et sur la ou chaque autre position circonférentielle du rotor entre deux pales de rotor directement voisines les lignes de séparation (26, 27) sont inclinées dans une deuxième orientation opposées à la première orientation comme la direction de montage par rapport à la direction axiale dans la direction circonférentielle.
  5. Rotor selon une des revendications 1 à 4, caractérisé en ce que radialement à l'extérieur dans la direction de vision le ou chaque segment d'élément de couplage (10, 10', 10") de chaque pale de rotor sur le premier côté (16) présente un contour tel que du côté d'entrée de flux voisin d'une arête d'entrée de flux (12) de la pale de rotor respective l'arête extérieure radiale (18) s'étendant essentiellement dans la direction axiale dépasse en saillie dans la direction circonférentielle par rapport à l'arête intérieur radiale (20) s'étendant essentiellement dans la direction axiale, tandis que sur ce premier côté (16) se détournant d'une arête de sortie de flux (13) de la pale de rotor respective, l'arête intérieure radiale (20) s'étendant essentiellement dans la direction axiale dépasse en saillie dans la direction circonférentielle par rapport à l'arête (18) extérieur radiale s'étendant essentiellement dans la direction axiale et en ce que le ou chaque segment d'élément de couplage (10, 10', 10") de chaque pale de rotor sur le deuxième côté (17) présente un contour tel que du côté de sortie de flux voisin de l'arête de sortie de flux (13) de la pale de rotor respective l'arête extérieure radiale (19) s'étendant essentiellement dans la direction axiale dépasse en saillie dans la direction circonférentielle par rapport à l'arête intérieure radiale (21) s'étendant essentiellement dans la direction axiale, tandis que sur ce deuxième côté (17)du côté d'entrée de flux se détournant de l'arête d'entrée de flux (12) de la pale de rotor respective l'arête intérieure radiale (21) s'étendant essentiellement dans la direction axiale dépasse en saillie dans la direction circonférentielle par rapport à l'arête extérieure radiale (19) s'étendant essentiellement dans la direction axiale.
  6. Rotor selon une des revendications 1 à 5, caractérisé en ce que sur le premier côté (16) et sur le deuxième côté (17) une surface couverte radialement de l'extérieur dans la direction de vision (28,29) respective et une surface visible radialement de l'extérieur dans la direction de vision (30,31) respective est réalisée, dans lequel sur le premier côté (16) la surface couverte radialement de l'extérieur (28) est positionnée du côté d'entrée de flux et la surface visible radialement de l'extérieur (30) est positionnée du côté de sortie de flux, et dans lequel sur le deuxième côté (17) la surface couverte radialement de l'extérieur (29) est positionnée du côté de sortie de flux et la surface visible radialement de l'extérieur (31) est positionnée du côté d'entrée de flux.
  7. Rotor selon une des revendications 1 à 6, caractérisé en ce que sur le premier côté (16) et sur le deuxième côté (17) du segment d'élément de couplage les lignes de séparation (26,27), qui séparent l'une de l'autre sur le premier côté (16) et sur le deuxième côté (17) la surface couverte radialement de l'extérieur (28,29) et la surface visible radialement de l'extérieur, ont une configuration dépourvue de point d'inflexion.
  8. Rotor selon une des revendications 1 à 7, caractérisé en ce que sur le premier côté (16) et sur le deuxième côté (17) du segment d'élément de couplage respectif vu dans la direction de vision le long des lignes de séparation (26,27) la surface couverte radialement de l'extérieur (28,29) par rapport à la direction radiale est inclinée d'un premier angle et la surface visible radialement de l'extérieur (30,31) est inclinée par rapport à la direction radiale d'un deuxième angle.
  9. Rotor selon la revendication 8, caractérisé en ce que sur le premier côté (16) et sur le deuxième côté (17) du segment d'élément de couplage respectif le premier angle et le deuxième angle sont proportionnellement de même grandeur et présentent des signes différents ou le premier angle et le deuxième angle sont proportionnellement de grandeur différente et présentent des signes différents.
  10. Rotor selon une des revendications 1 à 9, caractérisé en ce sur le premier côté (16) et sur le deuxième côté (17) du segment d'élément de couplage respectif la surface couverte radialement de l'extérieur (28,29) et la surface visible radialement de l'extérieur (30,31) sont de même grandeur et présentent ainsi un rapport de surface de 1 :1.
  11. Rotor selon une des revendications 1 à 9, caractérisé en ce que sur le premier côté (16) et sur le deuxième côté (17) du segment d'élément de couplage respectif la surface couverte radialement de l'extérieur (28,29) et la surface visible radialement de l'extérieur (30,31) sont de grandeur différente et présentent de préférence un rapport de surface de jusqu'à 1 :5 ou de jusqu'à 5 :1, notamment un rapport de surface de jusqu'à 1 :3 ou de jusqu'à 3 :1.
  12. Rotor selon une des revendications 1 à 11, caractérisé en ce que sur le premier côté et sur le deuxième côté (17) du segment d'élément de couplage respectif la surface couverte radialement de l'extérieur (28,29) et la surface visible radialement de l'extérieur (30,31) présentent des surfaces planes, aux contours en deux dimensions ou des surfaces incurvées spatialement, aux contours en trois dimensions.
  13. Rotor selon une des revendications 1 à 12, caractérisé en ce que sur le premier côté (16) et/ou sur le deuxième côté (17) du segment d'élément de couplage respectif dans la direction de vision radialement de l'extérieur l'arête radiale extérieure (18, 19) s'étendant dans la direction axiale et l'arête intérieure radiale (20,21) s'étendant essentiellement dans la direction axiale se recouvrent entièrement exclusivement à une position axiale.
  14. Rotor selon une des revendications 1 à 13, caractérisé en ce que chaque pale de rotor présente au niveau de sa pale radialement à l'extérieur un segment d'élément de couplage réalisé comme un segment de bande de recouvrement extérieur.
  15. Rotor selon une des revendications 1 à 14, caractérisé en ce que chaque pale de rotor présent au niveau de sa pale au moins un segment d'élément de couplage réalisé comme un segment d'élément de couplage intérieur.
EP11161987.0A 2010-07-12 2011-04-12 Rotor d'une turbomachine Not-in-force EP2410131B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102010031213A DE102010031213A1 (de) 2010-07-12 2010-07-12 Rotor einer Turbomaschine

Publications (3)

Publication Number Publication Date
EP2410131A2 EP2410131A2 (fr) 2012-01-25
EP2410131A3 EP2410131A3 (fr) 2017-08-02
EP2410131B1 true EP2410131B1 (fr) 2018-08-15

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EP11161987.0A Not-in-force EP2410131B1 (fr) 2010-07-12 2011-04-12 Rotor d'une turbomachine

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US (1) US8974186B2 (fr)
EP (1) EP2410131B1 (fr)
JP (1) JP5274625B2 (fr)
CN (1) CN102330572B (fr)
DE (1) DE102010031213A1 (fr)

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
ES2869338T3 (es) * 2011-10-07 2021-10-25 MTU Aero Engines AG Anillo de refuerzo de una paleta para una turbomaquinaria
US9347326B2 (en) * 2012-11-02 2016-05-24 General Electric Company Integral cover bucket assembly
JP6555344B2 (ja) * 2015-05-08 2019-08-07 株式会社リコー 光電変換素子
EP3297780B1 (fr) * 2015-05-20 2024-04-17 MAN Energy Solutions SE Procédé de fabrication d'un rotor de turbomachine
IT201900017171A1 (it) * 2019-09-25 2021-03-25 Ge Avio Srl Protezioni delle punte delle pale di turbina desintonizzate
CN114382555A (zh) * 2020-10-16 2022-04-22 中国航发商用航空发动机有限责任公司 导叶缘板、导叶、涡轮导向器及导叶缘板的设计方法

Family Cites Families (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
NL252407A (fr) 1960-05-09 1900-01-01
DE1159965B (de) 1961-08-10 1963-12-27 Bbc Brown Boveri & Cie Einrichtung zur Schwingungsdaempfung an einem Turbinen- oder Verdichter-Schaufelkranz
AT242717B (de) 1961-08-10 1965-10-11 Bbc Brown Boveri & Cie Deckbandbeschauflung für Turbinen oder Verdichter
US3923420A (en) * 1973-04-30 1975-12-02 Gen Electric Blade platform with friction damping interlock
GB2072760A (en) 1980-03-29 1981-10-07 Rolls Royce Shrouded turbine rotor blade
US4400915A (en) 1980-06-02 1983-08-30 United Technologies Corporation Fixture for restoring a face on the shroud of a rotor blade
US5001830A (en) * 1989-10-23 1991-03-26 Westinghouse Electric Corp. Method for assembling side entry control stage blades in a steam turbine
DE4015206C1 (fr) 1990-05-11 1991-10-17 Mtu Muenchen Gmbh
JPH0791206A (ja) * 1993-09-24 1995-04-04 Mitsubishi Heavy Ind Ltd 回転機械動翼のダンパ構造
JPH09209703A (ja) * 1996-01-31 1997-08-12 Mitsubishi Heavy Ind Ltd インテグラルシュラウド翼
DE10012381A1 (de) 2000-03-14 2001-09-20 Man Turbomasch Ag Ghh Borsig Schaufelschloss und Verfahren zur Herstellung eines Schaufelschlosses
US6910854B2 (en) * 2002-10-08 2005-06-28 United Technologies Corporation Leak resistant vane cluster
JP4335771B2 (ja) * 2004-09-16 2009-09-30 株式会社日立製作所 タービン動翼及びタービン設備
JP4869616B2 (ja) * 2005-04-01 2012-02-08 株式会社日立製作所 蒸気タービン動翼と蒸気タービンロータ及びそれを用いた蒸気タービン並びにその発電プラント
JP2007064074A (ja) * 2005-08-30 2007-03-15 Toshiba Corp 軸流タービン
EP1961918A1 (fr) 2007-02-21 2008-08-27 ABB Turbo Systems AG Roue de turbine
DE102009029587A1 (de) * 2009-09-18 2011-03-24 Man Diesel & Turbo Se Rotor einer Turbomaschine

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

Also Published As

Publication number Publication date
EP2410131A2 (fr) 2012-01-25
CN102330572B (zh) 2014-07-09
JP2012021529A (ja) 2012-02-02
DE102010031213A1 (de) 2012-01-12
US20120009067A1 (en) 2012-01-12
JP5274625B2 (ja) 2013-08-28
CN102330572A (zh) 2012-01-25
EP2410131A3 (fr) 2017-08-02
US8974186B2 (en) 2015-03-10

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